Aerospace structure having a cast-in-place noncompressible void filler

ABSTRACT

An aerospace structure and method for its construction composed of two elements having mutually opposed mating surfaces, at least one of which is irregular. The mating surfaces of the elements are fastened and compressed against a noncompressible cast-in-place void filler having complimentary shape to the two mating surfaces. The void filler is prepared by admixing a polymerizing matrix selected from polyesters, epoxides, polyamides, polyimides, polycarbonates, polyvinyl alcohols and organosilicone polymers and a space filling material selected from phenolic microspheres, carbon microspheres, metal coated microspheres, chopped fiberglass, alumina, fumed silica and mixtures thereof.

This invention relates to aerospace structures and methods of shimmingelements of these structures to their proper final contour.Specifically, this invention relates to graphite composite aerospacestructures having irregular, mutually opposed internal surfacesseparated by a cast-in-place, curable, noncompressible void filler. Thisinvention relates to aerospace structures and methods for aligning andjoining the same to form an integrated structure from a plurality ofelements. Specifically, this invention relates to joining elementscomposed of a graphite composite material at a location where theelements are juxtaposed along mutually opposing surfaces. This inventionfurther relates to a method for constructing an aerospace structure byinterposing a noncompressible, void filler between opposing compositesurface elements.

BACKGROUND OF THE INVENTION

Bonding stiff parallel surface panels to a resin core in order toproduce a lightweight yet strong structural sandwich has been known fora long time. Furthermore, curable resins that provide a range ofdensities and strengths, particularly those resins that provide a highstrength-to-weight or stiffness-to-weight ratio, have been used toproduce structural sandwiches. Long, U.S. Pat. No. 4,013,810, disclosesone such sandwich in which the resin core contains a mixture of resinand hollow glass microspheres. The resins disclosed by Long can bemolded into complex shapes suitable for use in aircraft flooring andengine nacelles. The sandwich panels disclosed by Long are composed of acompression molded thermosplastic resin fabricated under conditions ofhigh temperature and pressure and provide some capability forpostforming. Structures formed as described by Long are relativelystrong and lightweight but have a low compression strength ofapproximately 1,000 psi.

Lightweight resins such as epoxy or polyester resins having holloworganic or inorganic microspheres incorporated therein have beensuggested for use in several structural applications. Massey, U.S. Pat.No. 3,917,547, discloses polyurethane foams that have hollow silicamicrospheres incorporated in an organic polymeric matrix having improvedcompression strength. Similarly, both carbon and phenolic microsphereshave been incorporated in a variety of resins to produce lightweightmaterials having good insulation properties. Resins that incorporatemetal coated organic and inorganic particles or spheres to enhanceelectroconductivity or to prevent electromagnetic interference (EMI) andprovide radio frequency interference (RFI) shielding are also known. Forexample, U.S. Pat. No. 4,496,475 describes an electroconductive bodysuitable for use as termination elements for capacitors fabricated fromresins containing at least 10% by weight silver distributed betweensilver particles and inorganic silver coated spheres. U.S. Pat. No.4,566,990 discloses conductive thermoplastics in which fibers of glassor graphite are coated with aluminium, copper, silver, nickel, iron oralloys thereof. These metals are present in from 8 to 12% by weight andeffectively shield electronic equipment sensitive to EMI/RFI.

Many aerospace structures, such as selected elements of aerodynamicsurfaces including wing flaps and ailerons, are now composed ofcomposite structures. Current methods for fabrication of compositestructural components require that opposing surfaces of these elementsbe formed together, normally in an abutting relationship. Because theseelements are composed of composites, the tolerances to which these partscan be manufactured are not held to as strict a tolerance as isavailable for machined metal parts. Furthermore, one or more of thesurfaces of composite components are often irregular. As a consequence,when an aerospace structure is assembled from two of these compositestructural components with their smooth aerodynamic surfaces facingoutward, an irregular gap will exist between the two mated surfaces.This gap in the final aerospace structure is unacceptable becauselocalized overstressing is caused when, for example, the parts areriveted together. Filling the gap between the surfaces has beenachieved; however, current methods have several drawbacks. For example,one method involves hand-forming a solid shim from a material such asaluminium. Another method involves removing plys from a shim made of alaminated polymer until the required contour and shape are achieved.Both of these methods require trial fitting, removal, hand-shaping andrefitting of the shim until a satisfactory contour is achieved. Thesemethods are labor intensive, time-consuming and produce a nonstandardproduct that varies in quality with the skill of the mechanic. Often thecontour of the gap is complex, that is, it varies in thickness in bothdirections simultaneously and the gap cannot be adequately filled byeither method. Any gap remaining after shimming may result in localizeddistortion and stressing of the composite structure when the fastenersare installed.

SUMMARY OF THE INVENTION

The foregoing problems can be overcome by producing an aerospacestructure in which the two structural elements are fastened andcompressed against a noncompressible shim which has been complimentarilycontoured to conform to the irregularities in the abutting surfaces ofthe two structural elements. The correctly contoured shim is made of acurable cast-in-place polymer which, in its uncured state, cancompletely fill the void between the two mating surfaces. Thecast-in-place void filler is forced directly into the gap with theshimmed surfaces acting as two sides of the mold. The uncured voidfiller is suitably viscous to be forced into the gap between theirregular shimmed surfaces without draining the gap, thereby producingvoids prior to curing. Uncured void filler is injected into the gap fromthe opening nearest the leading ends of the shimmed surfaces, fillingthe gap and protruding from the trailing ends of the shimmed surfaces.The opening nearest the leading ends is then dammed with putty, whichacts as a temporary mold surface until the void filler cures. Uponcuring, the two surface elements of the aerodynamic structure arefastened together, compressing the irregular surfaces against the curedvoid filler. Since the resulting shim conforms exactly to theirregularities in the shimmed surfaces, thereby uniformly distributingthe stresses across the aerodynamic structure, excess cured void fillerprotruding from the trailing edge of the aerodynamic structure is thenshaped to meet the desired final contour.

Void fillers suitable for use in the present invention are preferablyheat stable, relatively noncompressible when cured, and have a highstrength-to-weight ratio. Compression strength must range from about2,000 to 30,000 psi and preferably in a range of from 5,000 to 25,000psi. Furthermore, void filler must retain their noncompressibility attemperatures ranging from -30° to 200° F. To achieve highstrength-to-weight ratios, the void filler contains a heat stablepolymerizing matrix. Polymerizing matrices most suitable for use in thepresent invention are epoxides, polycarbonates, polyvinyl alcohols,polyesters, polyamides, polyimides and organosilicon polymers, and, mostpreferably, epoxides. These polymerizing matrices are present in thevoid filler in a range of from 60 to 100% and preferably in a range offrom 80 to 90%. The balance of the resin is composed of space fillingmaterial necessary to achieve lightweight, electrochemical neutrality,or electrical conductivity. Suitable electrochemically neutral spacefilling material may be selected from phenolic resins, carbonmicrospheres, chopped fiberglass, alumina, fumed silica and mixturesthereof. When the aerodynamic elements of the aerospace structure arecomposed of graphite composite, it is preferred that theelectrochemically neutral spacing filling material be hollow or solidcarbon microspheres. When it is desired that the space filling materialbe electrically conducting, the carbon particles introduced into theresin are coated with metal. It is preferred that the metal coating beeither nickel, iron, copper, silver, silicon or mixtures thereof. To besuitably electrically conducting, the percent by weight of electricallyconducting metal in the void filler should be at least 1% and, mostpreferably, from 1 to 1.5%.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is an isometric view of the two elements of an aerodynamiccontrol surface structure, showing a gap between the two irregularsurfaces along which the elements will be joined;

FIG. 2 shows a side section of a tool and an aerospace structure beingjoined in accordance with the present invention with a noncompressible,curable void filler functioning as a shim customized precisely for theirregular surfaces; and,

FIG. 3 is a cross section of the aerospace structure with the twosurface elements fastened by a rivet to sandwich and compress theelements against the noncompressible void filler.

DESCRIPTION OF THE PREFERRED EMBODIMENT

The present invention provides a structure and method for joiningmutually opposing surfaces of aerospace structures. Examples ofaerospace structures that can be constructed in accordance with thepresent invention include structural control elements such as elevators,ailerons, rudders, and similar control surfaces. Normally, these controlsurfaces comprise a pair of surface skins that are separated andreinforced by internal structural elements. The upper and lower skinsmust then be joined at the leading ends and at the trailing ends. Theterm leading end, as used herein, describes that end of the structurenearest the leading edge of the control surface, and conversely, theterm trailing end describes that end nearest the trailing edge of thecontrol surface. The present invention is particularly adaptable forjoining trailing ends of control surfaces. For example, referring toFIG. 1, a partial view of the trailing end of a control surface includesupper skin element 10 and lower skin element 12. The upper surface ofupper skin element 10 forms an upper aerodynamic surface while the lowersurface of lower skin element 12 forms a lower aerodynamic surface. Theskins terminate at parallel trailing ends 14 and 16, respectively.Internally and forward of the trailing ends are mutually opposing,substantially parallel, spaced abutment surfaces 18 and 20. The abutmentsurfaces are irregular and will not fully contact each other when drawntogether by fasteners such as rivets. Therefore, in accordance with thepresent invention, a viscous curable void filler is injected into thespace between these two abutment surfaces, therein conforming to theirregularities of the mutually opposed abutting surfaces. The curablevoid filler is then cured and fasteners such as rivets 22 are applied todraw the trailing end regions of the skin elements tightly together toform an integral trailing edge.

Composite surface elements suitable for use in the present inventioninclude metals such as titanium and aluminum, as well as numerous alloysof those materials, and nonmetals such as fiberglass and epoxy graphitecomposites. The present invention is most suitable for use in connectionwith composite components.

Referring now to FIG. 2, an aerospace structure is constructed inaccordance with the present invention by placing the upper and lowerskin elements 10 and 12 between an appropriate tool 24 having upper andlower halves 26 and 27. The upper and lower skins are positioned in thetool 24 so that the upper and lower aerodynamic surfaces are held in adesired orientation, for example, in a converging relationship towardthe trailing end. The tool is designed so that the mutual abutmentsurfaces 18 and 20 adjacent to the trailing end of the structure arejuxtaposed in a spaced relationship. In accordance with the presentinvention, a viscous curable void filler 28 is then injected between theopposing interior surfaces so as to completely fill the space betweenthose surfaces. The void is injected in a rearward direction from theforward end of the opposing surfaces interior of the structural elementsrearwardly toward the trailing end. A sufficient amount is injected sothat the void filler extrudes beyond the trailing end of the structure.A damming material 29, such as putty or clay, is then positioned infront of the forward portion of the mutually opposed abutment surfacesto prevent the viscous void filler from escaping in a forward directionfrom the space between the opposing surfaces. The void filler is thenallowed to cure. Once cured, the damming material can be removed. Oncethe void filler is cured, the entire region or gap between the twoirregular, mutually opposed abutment surfaces will be in contact withthe surface of the cured void filler so that no gaps or voids exist.Once the void filler is cured, the aerospace structure can also bewithdrawn from the tool 24.

Referring now to FIG. 3, once the structure is removed from the tool 24,excess cured void filler extending beyond the trailing end can be shapedwith appropriate milling tools and the final contour of the trailing end31 is thereby produced. Thereafter, rivet holes can be drilled orotherwise formed adjacent the trailing end of the structure. The rivetholes are generally oriented transversely to the surfaces of thestructural elements. Portions of the rivet holes 32 adjacent thesurfaces are usually beveled so that an appropriate mating rivet head 33can mate with beveled portions of the holes to draw and compress theopposing elements to each other. Alternatively, opposing elements may befastened together against the noncompressible void filler withhard-fasteners, such as threaded or collared bolts. Preferably, the voidfiller is noncompressible so that no movement of the trailing edgeportions of the elements occurs when the rivets are inserted. Thus,since the void filler fills the entire space between the mutuallyopposing interior surfaces and since no movement of the elements takesplace upon insertion of the rivets, the stresses are evenly distributedacross the entire trailing end portion of the structure, eliminating theproblems associated with prior art.

The noncompressible, curable void filler suitable for use in accordancewith the present invention may be composed of a variety of polymerizingand space filling materials. The polymerizing materials are selectedfrom among those that are strong yet lightweight, and includepolyesters, epoxides, polyamides, polycarbonates, polyimides,polyetherimides, polyvinyl alcohol and organosilicone polymers.Formulations of these resins, together with their hardeners and spacefilling materials, are selected so that the proper viscosity and curingtimes are achieved. It is preferred that the curing time for the viscousvoid filler ranges from about 2 to about 8 hours, but it is mostpreferred that the curing time for the void filler ranges from about 3to about 5 hours. It is also most preferred that the polymerizing matrixbe a graphite epoxide. The viscosity of the noncompressible, curablevoid filler suitable for use in the present invention is that of a puttyor dough so that it can be easily worked into the space between theopposed abutment surfaces without rapidly draining therefrom.

The range of organic polymeric matrix in the curable, noncompressiblevoid filler suitable for use in accordance with the present inventionranges from 40% by weight up to 100% by weight. It is preferred,however, that the percent polymetric matrix in the curable,noncompressible void filler ranges from about 80 to 90%, with thebalance made up of a space filling material. Space filling materialssuitable for use in accordance with the present invention includephenolic microspheres, carbon microspheres, chopped fiberglass, alumina,fumed silica, metal coated carbon particles, and mixtures thereof. Thechoice of type and quantity of space filling material selected dependson the density required, adhesive and thermal properties desired,compressibility strength requirements and electrochemical neutrality orelectroconducting property desired. For example, density is decreased byusing increasing percentages by weight of hollow microspheres. Increaseddensities are achieved by using higher polymeric matrix percentages andsmaller percentages of hollow microspheres or increased percentages ofsolid microspheres, especially alumina, silica or metal coated solidmicrospheres. Densities suitable for use in accordance with the presentinvention range from about 40 to about 100 lb/ft³, with the preferredrange in densities being from 50 to 70 lb/ft³. Densities may also beincreased by mixing and curing the polymeric matrix resins under reducedatmospheric pressure. Conversely, densities are decreased by whippingair into the unpolymerized polymeric matrix.

It is essential that the void filler, when cured, be noncompressible. Ifthe compressibility strength of the void filler is below 2,000 psi, theaerospace structure will become too flexible and unsuitable for use as acontrol surface. Conversely, if the compressive strength is greater than30,000 psi, the void filler becomes too brittle and is predisposed tocracking and crumbling, again making the structure unsuitable for use asa control surface. Therefore, the range of compressive strengthssuitable for use in accordance with the present invention is from about2,000-30,000 psi. Suitable compressive strengths may be achieved byusing pure polymerizing matrix, for example, pure cured epoxide orpolyester. The density of these polymerizing matrixes, however, isfairly high, adding substantial weight to the aerospace structure. Itis, therefore, preferred that a space filling material of the typepreviously described be added to the polymerizing matrix to achieve thetargeted density and compression strength.

For secondary structural components such as horizontal and verticalstabilizers and spoilers, high resistance to compressibility and lateralsheer is desirable to achieve the proper strength and flightcharacteristics. The preferred compression strengths for thesestructures range from 15,000 to 25,000 psi. Since solid carbon and solidaluminum microspheres yield the highest compression strengths when addedas space filling material to void fillers, these particles are preferredfor this application. For example, a mixture of polymeric matrix andspace filling material preferred for use in accordance with the presentinvention would be a void filler composed of from 80 to 90% epoxide and10 to 20% solid carbon microspheres. Similarly, a preferred compositionfor the noncompressible, curable void filler containing solid aluminummicrospheres would contain from 85 to 90% epoxide and from 10 to 15%solid aluminum microspheres. Compression strengths for the epoxypolymeric matrix containing solid carbon microspheres would range from10,000 to 15,000 psi, and, in the case of solid aluminum microspheres,from 12,000 to 13,000 psi. On other areas of the aircraft, wherecompressibility and lateral sheer strength are not as important aslightweight, preferred space filling material would be selected fromphenolic fumed silica and hollow aluminum microspheres. Examples of suchaerospace structures would be landing gear doors where a preferrednoncompressible, curable void filler formulation would be epoxidecontaining from 13 to 18% phenolic microspheres. This would produce astructure having a compression strength of from 5,000 to 16,000 psi witha density of approximately 50 lbs/ft³. Similarly, examples of preferredcompositions of epoxy resin with fumed silica or hollow alumina would be5 to 8 percent fumed silica and 12 to 15 percent hollow aluminamicrospheres. These formulations would give compression strengths offrom 4,000 to 6,000 and from 5,000 to 6,000 for fumed silica and hollowaluminum microspheres, respectively.

Weight is also an important consideration in aerospace structures. Oncethe necessary compressibility strengths and lateral sheer strengths havebeen achieved, it is important to provide a lightweight void filler.Void filler densities suitable for use in accordance with the presentinvention range from about 40 to about 100 pounds per cubic foot. Forsecondary structural components, densities suitable for use inaccordance with this invention range from 45 to 100 pounds per cubicfoot, and it is preferred that densities range from 45 to 75 pounds percubic foot. In other areas of the aircraft requiring lowercompressibility and lateral sheer strengths, weight is a more importantconsideration, and densities of up to 60 pounds per cubic foot aresuitable for use in the present invention.

Electrochemical neutrality of the noncompressible void filler with themated surfaces and fasteners is often necessary to prevent corrosion andloss of structural integrity. Both the polymeric matrix and the spacefilling material must be electrochemically neutral with respect to agiven pair of surface elements and fasteners of the aerospace structure.For example, surface elements composed of graphite epoxy composite mayhave as their void-filling polymeric matrix either polyesters, epoxides,polyamides, polycarbonates, polyimides, polyetherimides, polyvinylalcohol or organosilicon polymers. Preferred polymeric matrixes includeepoxide and polyesters. Space filling material suitable for use innoncompressible, curable void fillers and which provide the necessaryelectrochemical neutrality include phenolic carbon and silicamicrospheres, chopped fiberglass alumina and mixtures thereof.

Preferred space filling materials suitable for use with graphitecomposite surface elements and epoxide or polyester polymeric matrixesinclude phenolic, carbon and aluminum microspheres. Preferrednoncompressible void fillers which provide electrochemical neutralityfor aerospace structures having fiberglass and polyaromatic amidesurface elements, are composed of epoxide and polyester polymericmatrixes and phenolic or carbon microspheres, chopped fiberglass orfumed silica. It is most preferred that noncompressible void fillershaving fiberglass surface elements contain epoxide polymeric matrixmixed with chopped fiberglass or fumed silica space filler. Foraerospace structures having polyaromatic amide surface elements, thepreferred composition of the non-compressible void filler is epoxidemixed with phenolic, chopped fiberglass or fumed silica space fillingmaterial. Examples of void filler compositions suitable for use inaccordance with the present invention when surface elements are composedof metal, include polyester, epoxide, polyamide, polycarbonate,polyimide, polyetherimide, polyvinyl alcohols and organo siliconpolymeric resins with or without space filling materials such asphenolic, carbon or fumed silica microspheres and chopped fiberglass oralumina. It is preferred that for metal surface elements, the aerospacestructure have a noncompressible, curable void filler composed ofepoxide or polyester polymeric matrix containing phenolic carbon orsilica microspheres as a space filling material.

In some instances it is important that the noncompressible, curable voidfiller adhere to the mutually opposed mated surfaces of the two surfaceelements. Suitable adherring polymeric matrixes suitable for use inaccordance with the present invention include polyesters, epoxides,polyamides, polycarbonates, polyimides, polyetherimides, polyvinylalcohols and organosilicon polymers. The preferred adherring polymericmatrixes include polyesters and epoxides. In some instances, it may alsobe desirable that the noncompressible, curable void filler beelectrically conducting. In these cases, the space filling material iscomposed of metal particles, metal-coated organic or inorganicparticles, and mixtures thereof. For example, in the case of graphitecomposite surface elements, it is preferred that the noncompressiblevoid filler be composed of graphite epoxy of from 8 to 20% by weightiron, copper, silver, silicon or nickel-coated carbon microspheres. Itis most preferred that secondary structural components having epoxycomposite surface elements have a noncompressible, curable void fillercomposed of epoxide resin and from 9 to 18% iron or nickel-coated carbonmicrospheres.

Examples

The following examples are included to assist one of ordinary skill inmaking and using the invention. They are intended as representativeexamples of the present invention and are not intended in any way tolimit the scope of this disclosure or the scope of protection granted byLetters Patent hereon. All parts and percentages referred to in thefollowing examples are by weight, unless otherwise indicated. Individualformulations may be varied to affect and alter the desired propertiesand characteristics.

Example 1

Rectangular graphite epoxy surface panels were selected for shimmingwith a curable void filler and subjected to compression testing. Eachcomposite surface panel had surface dimensions of approximately 2 in. by6 in. and a thickness of approximately 1/8th in. and had at least oneirregular surface. A curable void filler was prepared by adding 11 partsof epoxy hardener to 73 parts of an epoxy resin. These components werethen thoroughly mixed and 16 parts of hollow carbon microspheres wasadded to the mixture. These components were again thoroughly mixed andthe resulting viscous mixture was deposited on the irregular surface ofone graphite epoxy panel. The irregular surface of a second compositepanel was then pressed against the viscous void filler creating asandwich structure in which both internal surfaces were in contact overtheir entire surface with the void filler. The thickness of the viscousvoid filler in the sandwich structure was approximately 3/4 in. Thisstructure was then allowed to cure at ambient temperature for 4 hours.The graphite epoxy surface panels in the resulting structure stronglyadhered to the void filler. The cured void filler had a density of 50.3pounds per cubic foot and a compressive strength of 5,200 psi.

Example 2

An aerospace structure having a high density and high compressivestrength void filler suitable for use as a secondary structural elementwas made by the procedure described in Example 1. The void filler wascomposed of 35.5 parts epoxy resin and 5.2 parts epoxy hardener. To thiswas added 61.3 parts solid alumina silica microspheres. Upon curing,this noncompressible void filler had a density of 101 pounds per cubicfoot and a compressive strength of 16,200 psi.

Example 3

An aerospace structure having a noncompressible, curable void fillersuitable for use on landing doors was prepared as described in Example 1by combining 71.0 parts of epoxy resin with 10.7 parts epoxy hardener.To this was added 18.2 parts phenolic microspheres and the resultingmixture was vigorously mixed to entrap air. Upon curing, the density ofthe cured void filler was found to be 41.3 pounds per cubic foot with acompressive strength of 4,800 psi.

Example 4

An aerospace structure having a noncompressible, curable void filler wasprepared according to the procedures described in Example 1 by admixing74 parts of epoxy resin, 11 parts epoxy hardener, and 15 parts phenolicmicrospheres. The resulting mixture was deposited between epoxy graphitesurface panels as described in Example 1 and allowed to cure under areduced pressure of 28 torr. Upon curing, the noncompressible voidfiller was found to have a density of 54 pounds per cubic foot with anaverage compressive strength of 16,000 psi.

Conclusion

In summary, aerospace structures suitable for use in accordance with thepresent invention are easily fabricated and produce a standardizedproduct with excellent compression and lateral strength properties. Avariety of void fillers may be formulated to provide other desirableproperties such as low weight, electrical conductivity, electrochemicalneutrality, and adhesion to the surface elements.

Although the primary use of the present invention is currently producingaerospace control surface structures, the invention can also be employedto produce other aerospace and nonaerospace structures having irregular,mutually opposed surfaces requiring good compressibility and lateralsheer strengths. For example, landing gear doors and engine nacelles maybe fabricated using the present invention. In these cases greaterquantities of hollow microspheres may be incorporated with void fillerformulations to produce lightweight structures of suitable strength.

The present invention has been described in relation to a preferredembodiment thereof and several alternatives thereto. One of ordinaryskill, after reading the foregoing specification, will be able to effectvarious changes, substitutions of equivalents, and other alterationswithout departing from the broad concepts disclosed herein. It istherefore intended that the scope of Letters Patent granted hereon belimited only by the definition contained in the appended claims andequivalents thereof.

The embodiments of the invention in which an exclusive property orprivilege is claimed are defined as follows:
 1. An aerospace structurehaving aerodynamic surfaces positioned in a desired orientationcomprising:two structural elements, each of the structural elementshaving an aerodynamic surface and an abutting surface, the aerodynamicsurfaces being positioned in the desired orientation thereby positioningthe abutting surfaces in a mutually opposed spaced relationship, atleast one of the mutually opposed abutting surfaces being irregular; anoncompressible, crack-resistant shim comprising a cured void filler,the cured void filler complementarily contoured to conform to theirregularities of the abutting surfaces and sized to fill the spacetherebetween, the noncompressible shim sandwiched between the mutuallyopposed abutting surfaces, so that no voids exist; and, at least onefastener joining and compressing the abutting surfaces against thenoncompressible shim, the stresses in the structural elements adjacentthe abutting surfaces being evenly distributed.
 2. The structure asrecited in claim 1, wherein the void filler is an organic polymericmatrix comprising at least 40% by weight based on the total weight ofsaid void filler.
 3. The structure as recited in claim 2, wherein theorganic polymeric matrix is selected from the group consisting ofpolyesters, epoxides, polyamides, polycarbonates, polyimides,polyetherimides, polyvinyl alcohol and organosilicone polymers.
 4. Thestructure as recited in claim 3, wherein the organic polymeric matrix isan epoxide.
 5. The structure as recited in claim 2, wherein thenoncompressible curable void filler contains a space filling materialcomprising from 1% to 60% by weight based on the total weight of saidvoid filler.
 6. The structure as recited in claim 5, wherein said spacefilling material is electrical conductive.
 7. The structure as recitedin claim 6, wherein the electrical conductive space filling materialcomprises coated carbon particles, said coating being selected from thegroup consisting of nickel, iron, copper, silver and silicon.
 8. Thestructure as recited in claim 5, wherein the space filling material iselectrochemically neutral relative to both the matrix and the twoelements.
 9. The structure as recited in claim 8, wherein theelectrochemically neutral space filling material is selected from thegroup consisting of phenolic microspheres, carbon microspheres, metalcoated carbon microspheres, chopped fiberglass, alumina, fumed silica,and mixtures thereof.